RU2445233C2 - Aircraft fuselage and aircraft - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft fuselage and aircraft. Proposed fuselage comprises floor to divide aircraft inner space into bottom compartment and top compartment. Floor comprises segments arranged in two rows along aircraft fuselage. Floor segments may be jointed together to form self-supporting structure. Floor segment comprises top and bottom partitions arranged to form hollow space there between to accommodate aircraft fuselage system elements, jointing element to be jointed to another jointing element of another floor segment to make joint there between. Air conditioning pipeline extends along floor segments length and has several outlets to feed conditioned air into passenger cabin.

EFFECT: reduced weight.

24 cl, 3 dwg

Description

Technical field

The present invention relates to a floor segment of vehicles, in particular an aircraft, for dividing the interior into upper and lower. In addition, the invention relates to vehicles having a floor that divides the interior into upper and lower, if the floor includes at least two segments of the aforementioned type.

BACKGROUND OF THE INVENTION

The requirements for the efficiency and economy of modern passenger aircraft dictate the need to optimize the internal space. The space occupied by each passenger individually is directly related to its comfort in flight.

An additional important factor in the efficiency of a passenger aircraft is the payload provided by the aircraft concerned. With a constant take-off mass of the aircraft, an increase in commercial load can be achieved, in particular, if the so-called system mass and mass of consumables are kept as low as possible.

In this context, the term "systemic mass" refers to the mass necessary to equip a modern passenger aircraft. This includes, for example, a host of drinking and process water systems, air conditioning systems and electrical equipment, such as, for example, video recorders, monitors and audio systems. With regard to the term "mass of consumables", here, in particular, refers to the mass of the on-board fuel supply.

Improving the efficiency of modern aircraft engines, as well as their improved aerodynamic qualities, partially reflect the above requirements. However, further modernization can only be achieved by changing the architecture of the aircraft. This applies to the rational choice and location of the elements necessary to equip the interior of the aircraft.

SUMMARY OF THE INVENTION

The aim of the present invention is the provision of a modernized interior architecture, in particular passenger aircraft, which is an important factor in increasing the commercial load and the volume of internal space.

This problem is solved by the floor segment of vehicles in accordance with the present invention.

The aforementioned floor segment is used to divide the interior space of vehicles into lower and upper. The floor segment includes an upper partition and a lower partition, between which there is an empty space. This space is designed to accommodate vehicle system components.

The proposed floor segment is based on the idea that an increase in the usable space of the passenger compartment can be achieved if system elements are installed between the two partitions. With this design, the floor segment is a hollow body. However, there is no need to seal the hollow body from the environment. On the contrary, the partitions may have openings and recesses for access to the hollow space from the outside.

Hereinafter, the term "system elements" refers to all elements that are part of the equipment of modern passenger aircraft that have a direct or indirect effect on the level of passenger comfort. Thus, the elements of the systems include not only the entire drinking water supply system and sewage system, elements of the air conditioning system and electronic devices, but also supply and mixing lines for liquids and / or gases and electric and / or optical lines for monitoring and adjusting the electrical equipment located in passenger compartment. In addition, the term “system elements” also includes data and communications devices that can be used by passengers and / or aircraft crew.

Further, the above-described floor segment is based on the idea of creating inside the aircraft a special space for system elements that are preferably permanently mounted in the interior of the aircraft. Thus, the maximum possible degree of separation between the useful areas of the passenger compartment intended for passengers and the areas occupied by system elements mounted on board can be realized. This space allocated for system elements is provided by the empty space of a floor segment having a multilayer structure from the upper and lower partitions. In particular, in the design of the floor, consisting of many segments, an empty space of a sufficiently large size is created to accommodate all the elements of the systems needed in the cabin.

It is preferable to design the individual floor segments in such a way as to provide a continuous empty space, overlapping in the longitudinal and transverse directions of the entire area of the cabin or at least a large part of the area of the cabin.

Compared with the production of conventional aircraft, the above-described floor segment can significantly reduce labor costs when installing internal equipment and interior equipment, which provides significant savings in time and costs for the manufacture of aircraft. In the case of a conventional aircraft, the construction of passenger compartments and the construction of system elements are completely separate. After creating the fuselage segments as part of the so-called assembly of the structure, these fuselage segments are equipped with the appropriate system settings in the process of creating interior architecture. This occurs before the connection of individual segments into a single fuselage of the aircraft at the final stage. Only after this is the installation of the wings, tail, engines and chassis performed, resulting in a complete aircraft.

Compared with conventional installation using the above-described floor segments, individual passenger compartments and the equipment of the systems necessary for them can be created at a single working stage. This reduces the above labor costs when installing passenger compartment equipment.

In accordance with the invention, the upper and lower partitions form a self-supporting structure with an empty space between them. An advantage of this design is that the floor segment does not require external supports, and thus, both the effective space above the floor segment and the space under the floor segment are not reduced by any supporting structures.

In accordance with a further development of the invention, the floor segment also includes a connecting element, the design of which allows its articulation with another connecting element of another floor segment, creating a mate between these floor segments. This pairing allows you to create a winning modular design of individual floor segments. An advantage of this solution is the possibility of arbitrary combination of different floor segments on an aircraft, especially where the fuselage has the same diameter. As for the upper cabin, it is possible to easily ensure the multivariance of the equipment of the passenger compartment, if during the installation of the floor, combining many segments, there are corresponding different floor segments.

Thus, the above-described floor segment contributes to a significant reduction in the time spent on installing or refitting the aircraft interior architecture. At the same time, the option of placing system elements inside individual floor segments, described above, allows you to increase the passenger compartment space. In addition, greater flexibility is achieved in terms of equipment for the interior of an individual aircraft.

In accordance with a further development of the invention, an interface for a wire of gases or liquids is designed, which allows mounting lines for supplying liquids and gases in the entire area of the passenger compartment.

In accordance with a further development of the invention, an interface has been designed for laying electrical and / or optical lines. Such lines may be, for example, control lines, data lines or communication lines, as well as power lines. Power lines are power supply lines, in particular current supply lines. Optical lines are, in particular, fiberglass cables, which in modern vehicles increasingly provide interference-free data transmission within the respective vehicle. The interface is designed as a quick coupler. Thus, a simple insert provides a connection between different segments of the floor.

An interface device is provided on the outer surface of the floor segment, which is designed in such a way that one floor segment and the other floor segment can be connected to each other only in a certain relative position. This in the simplest way prevents an erroneous flipping of a floor segment by 180 ° when mounting a floor consisting of many segments. In this way, it is easy to avoid mounting the floor with the floor segments flipped upside down.

The floor segment may include at least one channel located in the cavity, intended for laying lines. In this context, the term "lines" refers to both electric and optical lines, which, in particular, are used for data transmission. Similarly, the term “lines” also includes pipelines for pumping liquids and / or gases. Liquid pipelines are used, in particular, for the supply of drinking water or the removal of process water. In the case of an aircraft, gas pipelines are used, in particular, for a centralized air conditioning system or emergency oxygen supply system.

In particular, in the modular design of the floor segments, closed channels for supplying liquids and gases can be easily integrated without using separate pipes. For these purposes, it is advisable to provide such channels with surface coatings corresponding to a specific purpose.

It must be emphasized that for ease of maintenance, channels equipped in the cavity are accessible through openings in the upper and / or lower partition.

The floor segment may contain at least one dividing element, partitioning the cavity into at least two secondary cavities. In this design solution, the secondary cavities can be provided commensurate with the devices installed in them, for example, fuel compartments, valves, actuators, pumps, etc. Access to these devices is possible from above or below through openings in the upper or lower partition. In addition to system elements, it is also possible to install electronic devices in the floor segment, which are part of the on-board multimedia entertainment system and / or passenger information system.

The floor segment may also comprise a container for storing gases and / or liquids. This allows for compact, economical in area and safe placement of the respective containers. The container may, in particular, be equipped in a secondary cavity.

As previously explained, a gas cylinder may, in particular, be used to store an emergency supply of oxygen in a passenger aircraft. The liquid tank may, in particular, be suitable for storing drinking or industrial water.

The floor segment may also include a container for storing items of luggage and / or equipment. Thus, the floor segments provide space saving and safe placement of items of baggage and equipment as well, in which the accidental fall of such items becomes impossible even in an extremely turbulent flight area.

A container for storing items of baggage and / or equipment may in particular be equipped in a secondary cavity.

In accordance with a further development of the invention, the floor segment comprises an upper structure extending upward from the upper partition and / or a lower structure extending downward from the lower partition. The upper structures can be entire installations, such as, for example, a kitchen, a toilet with or without a toilet, or a toilet with or without a shower. The lower structures may be installations used, for example, for the safe storage of items of luggage in the ceiling of the lower passenger compartment or for fastening cargo packages on the ceiling of the lower cargo compartment.

The upper partition and / or lower partition of the floor segment comprises a rail system. In particular, on the upper partition, such a rail system makes it easy and reliable to secure passenger seats. Rails on the lower partition can be used, for example, to attach ceiling devices that allow you to install fasteners of various configurations that can be used to fix items of luggage, providing a high degree of safety during transportation.

There is at least one connection point in the upper / lower partition. In this context, the connection point may be a mechanical fastener, which, being the so-called reinforced attachment point, allows forces to be applied to the floor segment without breaking or damaging the floor segment. Such efforts are caused, for example, by large moving loads or stationary installations.

With the proposed design of the determined fasteners, it is thus possible to assemble stable floor segments even with a relatively low weight.

The connection point, however, can also be an electrical or optical connector for connecting a control line and / or a communication line.

In addition, the pneumatic coupling may also be a connection point. Thus, the connection of the gas pipeline and / or pipeline can be carried out not only on the sides of the floor segment, but also on the partitions.

A floor segment may comprise a lighting element. This makes it possible to provide a simple and, in particular, compact way, illumination of the back space due to the placement of the lighting element in the lower partition.

Accordingly, illumination of the upper space can be achieved by mounting the corresponding floor lighting elements in the upper partition of the floor segment.

The floor segment may also include a wiring layer. Such a layered design of the electrical circuit allows for compact placement of electronic elements. It is preferable to realize the electrical circuit by means of a printed circuit integrated into the floor segment in a certain compact manner.

The use of a printed circuit has the advantage that communication lines, control, power supply, etc. can be laid in layers of the floor segment closest to the surface.

A floor segment may contain at least one heating element. This allows for compact placement of the space heater and / or cargo compartments with a corresponding increase in usable space for passengers.

The object of the invention is also a vehicle that contains a floor for dividing the interior of the vehicle into lower and upper, and the floor consists of at least two segments in accordance with one of the above technical solutions.

The idea of the above vehicle is based on the fact that an increase in usable space, in particular, in the passenger compartment, can be achieved if the floor of the aircraft is constructed in the form of a hollow body. Such a floor can be used for placement of interior systems, as well as for laying transmission lines for liquid, gases, electricity, as well as control and communication signals.

In this context, the term “floor” of an aircraft refers to a dividing structure between different levels of the vehicle’s interior. In an aircraft, the floor can thus provide a spatial separation of the passenger compartment from the cargo compartment or a spatial separation of the upper passenger compartment from the lower. The floor consists of several segments having the same or compatible sizes, so that by joining the segments, a solid floor can be constructed. During the initial installation or conversion of the vehicle, such a modular floor, consisting of a number of segments, can significantly reduce the labor costs associated with the construction of the interior architecture.

If the individual floor segments have the same size and shape, this allows you to assemble a floor in which the individual segments form the correct system. In the case where the individual floor segments have different sizes, the optimal fit of the floor into the fuselage geometry can be achieved if the individual segments are compatible with each other. The concept of compatible sizes suggests that the side faces of floor segments have lengths, the ratio of which is expressed by small integers.

The individual floor segments functionally depend on the corresponding location in the floor system. The advantage of this solution is that the design or modification of the interior architecture of the corresponding vehicle is carried out quickly with an elegant and effective consideration of the constraints dictated by the spatial position of the corresponding floor segments in the floor structure.

The combination of adjacent floor segments forms a self-supporting structure. The advantage of this solution is the lack of the need to provide an average floor support without compromising the stability of the floor, consisting of several segments. In turn, this provides free access to the lower space, which can be used, for example, as a cargo compartment for large objects, which are not hindered by any mechanical supports.

The self-supporting structure is connected to the inside of the vehicle fuselage in such a way that when a floor segment is subjected to a load, at least one attachment point between the fuselage and the self-supporting structure works to transfer the load from the self-supporting structure to the fuselage. Due to this, the forces created, for example, by the large weight of the floor, can be transmitted to the fuselage of the vehicle. Thus, the stability of a floor consisting of several segments is increased.

The self-supporting structure is connected to the inside of the aircraft fuselage in such a way that when the fuselage is loaded, at least one attachment point between the fuselage and the floor works to transfer the load from the fuselage to the self-supporting structure. Thus, the floor, consisting of several segments, helps to increase the rigidity of the fuselage structure.

In one possible embodiment of the invention, the lower space of the vessel is the cargo compartment, and the upper space is the passenger compartment. In this configuration, in the cavity formed by the floor segments between the cargo compartment and the passenger compartment, it is possible to place various system elements necessary for equipping the passenger compartment space, cargo compartment, or both.

In another embodiment, the lower space of the vessel is the lower cabin, and the upper space is the upper cabin. Thus, a floor consisting of several segments can also be used in the case of wide-body passenger aircraft having several passenger levels.

The vehicle may have an additional floor for dividing the lower space or the upper space. In this configuration, the additional floor also consists of at least two of the above segments.

Thus, the aforementioned floor segments can be used in the installation of several floors located one above the other in large vehicles.

The indicated vehicle may be an aircraft, in particular an aircraft. On an aircraft, in particular on a modern aircraft providing a high level of comfort for passengers, many system elements are required. Thus, the aforementioned floor, consisting of a set of elements, is particularly suitable for accommodating a variety of system elements, ingeniously solving the problem of increasing the internal space of an aircraft for both passengers and cargo.

The purpose of the invention is further realized through the use of the above floor element on a vehicle, in particular an aircraft.

Brief Description of the Drawings

The advantages and parameters of the present invention are set forth in the following typical description of a technical solution, which is currently preferred. The figures schematically show:

Fig. 1 - the design of the floor, consisting of a set of segments overlapping the entire internal space of the aircraft;

Fig. 2 is a sectional view of the aircraft fuselage, where the interior of the aircraft is divided by a floor consisting of several segments;

Fig. 3 - a combination of two floor segments, with elements of systems located in the cavities of the segments.

DETAILED DESCRIPTION OF THE INVENTION

It should be noted that in the figures identical or corresponding elements are indicated by the same item numbers.

Figure 1 shows a possible technical solution, where almost the entire longitudinal length of the aircraft fuselage extends the floor of an 80-module design, separating the cargo compartment below the passenger compartment above it. The floor consists of 16 segments, indicated by reference numbers from 1 to 16. As shown in Fig. 1, the floor segments along the center line of the fuselage are arranged in two rows, and the width of the segments provides complete overlap of the fuselage also in width.

The design of the individual floor segments provides a self-supporting structure when they are connected by the front sides. The modular construction of the floor is ensured by the overall dimensions of individual segments 1-16, of which segments 3-14 have the same dimensions. Depending on the desired configuration of the interior of the aircraft, it is possible to place different segments of the floor in a specific position in the floor structure.

Fig. 2 shows a view of the aircraft fuselage in section 50, with floor 80. Floor 80 divides the internal space of the aircraft fuselage 50 into the cargo compartment 70 located below and the passenger compartment 60 located above it.

In this technical solution, the passenger cabin 60 is equipped with a system of seats 61, which, by means of devices not shown in the figure, are attached to the guide system 63, so that even in turbulent sections of the flight, the seats 61 are securely mounted. The passenger cabin 60 also has a shower cabin 62, which, according to the shown typical technical solution, is located on the right side of the passenger compartment 60. In addition, connection points 64 are equipped in the passenger compartment 60, each connection point 64 p it is a mechanical fastening element for goods (not shown) carried in the passenger compartment 60. Connection points 64 may also be electrical and / or optical connectors allowing lines to be drawn from the hollow space 30 formed between the upper partition 81 and the lower partition 82 by two floor segments 80a and 80b. The hollow space 30 is designed to accommodate 80 elements of systems inside the floor, which are described in more detail below with reference to Fig. 3.

Cargo compartment 70 includes a loading platform 71, designed to accommodate cargo. In addition, the lower structure 72 is provided on the lower partition 82 from the floor 80 to the inside of the cargo compartment 70. The lower structure 72 can be used to secure loads using devices not shown in the figure.

The first floor segment 80a includes a connecting element 84a, the design of which provides a mating connection with the connecting element 84b of the second segment of the floor 80b. Two connecting elements 84a and 84b form a defined pair 84.

It is advisable to place the connecting elements 84a and 84b, as well as other connecting elements of the floor segments (not shown) in certain positions, so that a complete modular floor structure 80 can be assembled from several segments (see Fig. 1). Built-in system elements can fill the entire hollow space 30 along the horizontal axis of the floor 80.

In addition, on the lower partition 82 there is a connection point 85 having the same purpose as the connection point 64 described above, located on the upper partition 81.

The floor 80 is attached to the fuselage at two connection points 86. Since the floor 80 is a self-supporting mechanically stable structure, it also increases the rigidity of the fuselage 50. Thus, the fuselage 50 and the floor 80 together form both a rigid fuselage 50 and a stable floor 80, consisting of several segments 80a, 80b.

Figure 3 shows a plan view of two segments 11 and 13 (see Fig. 1). In this configuration, the upper partition of the two floor segments 11 and 13 is not shown, therefore, all the elements of the systems located in the hollow space formed by the two floor segments 11 and 13 are visible.

It must be clearly understood that the technical solution, presented, in particular, in Fig. 3, is only one of the possible solutions, chosen arbitrarily from the many possible solutions of the invention.

In the hollow space 30, formed between the two segments of the floor 11 and 13, there is a drinking water supply pipe 20 connected to the pump 32. The pump 32 is located in the segment of the floor 13. In both segments of the floor 11 and 13, the waste water 21 passes through the entire length, consisting of two sections, which at the border of two floor segments 11 and 13 are connected by a corresponding docking device.

In addition, along the entire length of the two floor segments 11 and 13 passes the pipeline of the air conditioning system 22, including several exits 26, designed to supply air conditioning to the passenger compartment.

The wastewater outlet 21 has a wastewater valve 25, equipped in the floor segment 11. The drinking water supply pipe 20 is equipped with a shut-off valve 23, which is also available in the floor segment 11. Both the shut-off valve 23 and the wastewater valve 25 are connected to the valve control unit indicated by 24.

Both segments of the floor 11 and 13, in addition, are interconnected by several electrical lines, including the power line 27, data line 28 and communication line 29.

In addition, the floor segment 13 includes a hollow space 41 formed by a dividing element 31a. The hollow space 41 is designed to accommodate electrical devices, such as a drinking water pump 32, as well as a control unit 33 connected to the pump 32.

In addition, a drain valve 34 is provided in the hollow space 31, which is located in the drinking water tank 35 and can be actuated by the control unit 33. By opening the drain valve 34, the negative pressure in the drinking water tank 35 caused by the removal of drinking water using the pump 32 can be compensated by air intake accordingly.

In addition, the floor segment 13 has a hollow space 36 formed by a dividing element 36a. This hollow space can be used to place items of luggage or items of equipment from the passenger compartment (not shown here).

Thus, in this application segments of the floor 11, 13 of vehicles, in particular aircraft, are provided for dividing the interior into a lower space 70 and an upper space 60. The floor segment 11.13 includes an upper partition 81 and a lower partition 82, between which hollow space 30, designed to accommodate elements of vehicle systems 20-29, 32-35. The modular design of the floor segments is preferred so that the individual segments 11, 13 in floor structure 80 can be replaced with other floor segments 11, 13 having the same or compatible sizes and connections for system elements.

List of item numbers

1-16 Floor segments twenty Drinking water pipeline 21 Sewage discharge 22 Air conditioning pipe 23 Shutoff valve 24 Valve control unit 25 Waste water valve 26 Conclusions of the air conditioning pipeline to the passenger compartment 27 Power line 28 Data line 29th Communication line thirty Hollow space 31 Hollow space for equipment 31a Separation element 32 Potable water pump 33 Pump control unit 32 34 Drain valve 35 Drinking water tank 36 Hollow space 36a Separation element fifty Fuselage 60 Passenger compartment 61 Armchairs 62 Shower stall 63 Guide system 64 Junction point 70 Cargo hold 71 Loading pad 72 Bottom construction 80 Floor with integrated system elements 80a First floor segment 80b Second floor segment 81 Upper partition 82 Lower partition 84 Air conditioning pipe connection device 84a Connecting element 84b Connecting element 85 Junction point 86 Connection point, floor - fuselage 87 Pairing electrical lines

Claims (24)

1. The aircraft fuselage comprising a floor for dividing the interior of the aircraft fuselage into the lower space (70) and the cabin space (60), the floor comprising floor segments (11, 13) installed in two rows in the longitudinal direction of the aircraft fuselage, and these floor segments have a structure that allows them to be connected to each other with the formation of a self-supporting structure, and each floor segment contains an upper partition (81) and a lower partition (82), between which a hollow space (30) is formed, intended Designed to accommodate the elements of the aircraft fuselage systems (20-29, 32-35), at least one connecting element (84a) connected to another connecting element (84b) of another floor segment (13), creating a pair (84, 87) between the segments of the floor (11, 13), while along the length of the floor segments (11, 13) passes the pipeline of the air conditioning system (22) with several outlets (26) designed to supply air conditioning to the passenger compartment. 2. The fuselage according to claim 1, which provides for pairing for pipelines of gases and liquids. 3. The fuselage according to claim 1 or 2, which provides for pairing for laying electrical and / or optical lines (27, 28, 29). 4. The fuselage according to claim 1, in which the pairing (84, 87) between the segments of the floor is made in the form of a quick coupling. 5. The fuselage according to claim 1, further comprising at least one channel that is laid in the hollow space (30) and is intended for laying lines (27, 28, 29). 6. The fuselage according to claim 1, further comprising at least one dividing element (31a, 36a) dividing the cavity (30) into at least two parts. 7. The fuselage according to claim 1, wherein the floor segment further includes a reservoir (35) for storing gases and / or liquids. 8. The fuselage according to claim 1, wherein the floor segment further includes a container for items of luggage and / or equipment items. 9. The fuselage according to claim 1, wherein the floor segment further includes an upper structure (62) extending upward from the upper partition (81) and / or a lower structure (72) extending downward from the lower partition (82). 10. The fuselage according to claim 1, in which the upper partition (81) and / or lower partition (82) of the floor segment has a guide system (63). 11. The fuselage according to claim 1, in which the upper partition (81) and / or the lower partition (82) of the floor segment has at least one connection point (64, 85). 12. The fuselage according to claim 1, in which the floor segment further includes at least one lighting element. 13. The fuselage according to claim 1, in which the floor segment further includes a layer with an electrical circuit. 14. The fuselage according to claim 1, in which the floor segment further includes at least one heating element. 15. An aircraft having a fuselage made according to any one of claims 1 to 14. 16. The aircraft according to claim 15, wherein the floor (80) consists of several segments (3-14) having the same or compatible sizes, and the connection of the floor segments (3-14) forms a continuous floor (80). 17. The aircraft according to clause 16, in which individual floor segments (1-16) functionally depend on the corresponding location of the segment (1-16) in the floor structure (80). 18. The aircraft according to 17, in which the combination of floor segments (1-16), located side by side, forms a self-supporting structure (80). 19. The aircraft according to claim 18, wherein the self-supporting structure (80) is connected to the inside of the fuselage (50) of the aircraft in such a way that when the floor segment (1-16) is subjected to a load, at least one connection point (86) ) between the fuselage (50) and the self-supporting structure (80) serves to transfer the load from the self-supporting structure (80) to the fuselage (50). 20. The aircraft according to claim 19, in which the self-supporting structure (80) is connected to the inside of the fuselage (50) of the aircraft in such a way that when the fuselage (50) is subjected to a load, at least one connection point (86) between the fuselage (50) and a self-supporting structure (80) serves to transfer the load from the fuselage (50) to the self-supporting structure (80). 21. The aircraft according to one of paragraphs.15-20, in which the lower space is the cargo compartment (70). 22. The aircraft according to one of paragraphs.15-20, in which the lower space is the lower cabin, and the upper space is the upper cabin. 23. The aircraft according to clause 15, further comprising another floor for dividing the lower space or upper space, and the additional floor consists of at least two segments. 24. The aircraft according to clause 15, which is an aircraft.

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